Ins alignment method using a doppler sensor and a GPS/HVINS

• US 6,094,163 A
• Filed: 01/21/1998
• Issued: 07/25/2000
• Est. Priority Date: 01/21/1998
• Status: Expired due to Fees

• Current Assignee: Min-I James Chang
• Original Assignee: Min-I James Chang
• Inventors: Chang, Min-I James
• Primary Examiner(s): Tarcza, Thomas H.
• Assistant Examiner(s): PHAN, DAO LINDA
• Application Number:
  US09/009,918
• Time in Patent Office: 916 Days
• Field of Search: 342/357, 342/352, 455/12.1, 701/213, 701/220
• US Class Current: 342/357.59
• CPC Class Codes: G01C 21/1652 with ranging devices, e.g. LIDAR or RADAR
• CPC Class Codes: G01C 21/1654 with electromagnetic compass
• CPC Class Codes: G01S 5/0247 Determining attitude

Abstract

Transfer/in-flight alignment technique using a Doppler velocity sensor. An aircraft navigation system (10 and/or 20), a Doppler velocity sensor (50) and an alignment filter (45) are used to align the inertial navigation system (4) of a slave vehicle. The velocity (and/or position) of the aircraft navigation system, the velocity (and/or position) of the slave vehicle'"'"'s inertial navigation system (40) and the velocity measurement of a Doppler velocity sensor (50) are used to generate the measurements of the alignment filter (45). The DVS and aircraft navigation system are used simultaneously to align the inertial navigation system of the slave vehicle. A GPS receiver (60) with a GPS antenna (70), a Doppler velocity sensor (50) and an alignment filer (46) are used to align the inertial navigation system (40) of a flight vehicle. The velocity (and/or position) of a GPS receiver (60), the velocity (and/or position) of the inertial navigation system (40) of a flight vehicle and the velocity measurement of a Doppler velocity sensor (50) are used to generate the measurements of the in-flight alignment filter (46).

Claims

1. A transfer alignment system for aligning an inertial navigation system of a slave vehicle comprising:

an inertial navigation system installed in the slave vehicle and providing the position, velocity and attitude of the slave vehicle;

a Doppler velocity sensor installed in the slave vehicle and providing the velocity of the slave vehicle with respect to a coordinate system fixed to the body of the slave vehicle;

one of an inertial navigation system and an integrated global positioning system/inertial navigation system installed in an aircraft carrying the slave vehicle and providing the position, velocity and attitude of the aircraft; and

a transfer alignment filter updated by a velocity measurement of the Doppler velocity sensor and at least one of the velocity and the position of a host aircraft navigation system.

2. The system according to claim 1 wherein the transfer alignment filter is a Kalman filter, a least square filter or a combination of a Kalman filter and a least square filter.

3. The system according in claim 1 wherein the inertial navigation system comprises 3 accelerometers, 3 gyros and a flight computer that computes the position, the velocity, and the attitude of the slave vehicle, updates the alignment filter, and performs the guidance and control functions of the slave vehicle.

4. The system according to claim 1 wherein the inertial navigation system is initialized by the aircraft navigation system, by a magnetic detector or by a gyrocompass.

5. The system according to claim 1 wherein the transfer alignment filter is updated by at least one of:

the difference of the instantaneous velocity measurements of the Doppler velocity sensor and the instantaneous velocity of the aircraft navigation system or the inertial navigation system of the slave vehicle;

the difference of the average velocity measurements of the Doppler velocity sensor and the average velocity of the aircraft navigation system or the inertial navigation system of the slave vehicle;

the difference of the instantaneous velocity of the aircraft navigation system and the instantaneous velocity of the inertial navigation system of the slave vehicle;

the difference of the average velocity of the aircraft navigation system and the average velocity of the inertial navigation system of the slave vehicle;

the difference of the incremental position of the aircraft navigation system and the average velocity of the inertial navigation system of the slave vehicle;

the difference of the position of the aircraft navigation system and the position of the inertial navigation system of the slave vehicle.

6. The system as recited in claim 1 wherein the transfer alignment filter uses a Cartesian coordinate system or a coordinate system fixed to the body of the slave vehicle.

7. The system according to claim 5 wherein the transfer alignment filter measurement uses at least one of a linear function of alignment error, a reference velocity error of the Doppler velocity sensor and errors of the inertial sensor of the slave vehicle.

8. The system according to claim 7 wherein the reference velocity is a velocity obtained from the aircraft navigation system or a velocity computed by the inertial navigation system of the flight vehicle and updated by the aircraft navigation system.

9. An in-flight alignment system for aligning an inertial navigation system of a flight vehicle such as an aircraft or a missile or a guided bomb or an unmanned air vehicle, said system comprising

an inertial navigation system installed in a flight vehicle and providing the position, velocity and attitude of the flight vehicle;

a Doppler velocity sensor installed in the flight vehicle and providing the velocity of the flight vehicle with respect to a coordinate system fixed to a body of the flight vehicle;

a global position system receiver installed in the flight vehicle, and providing velocity and position of the flight vehicle with respect to a navigation coordinate system;

a global positioning system antenna mounted on the flight vehicle and providing a global positioning system signal to the global positioning system receiver;

an in-flight alignment filter updated by the velocity measurement of the Doppler velocity sensor, and at least one of the velocity and the position of the global positioning system.

10. The system according to claim 9 wherein the alignment filter is a Kalman filter, a least square filter or a combination of a Kalman filter and a least square filter.

11. The system according to claim 9 wherein the inertial navigation system comprises 3 gyros, 3 accelerometers and a flight computer that computes the position, velocity and attitude of the flight vehicle, updates the in-flight alignment filter, and performs navigation, guidance and control functions of the flight vehicle.

12. The system according to claim 9 wherein the inertial navigation system is initialized by a magnetic detector or a gyrocompass.

13. The system according to claim 9 wherein the alignment filter is updated by at least one of:

the difference of an instantaneous velocity measurements of the Doppler velocity system and the instantaneous velocity of the global positioning system,

the difference of an average velocity measurements of the Doppler velocity sensor and an average global positioning system velocity;

the difference of an instantaneous global positioning system velocity and an instantaneous velocity computed by the inertial navigation system of the flight vehicle;

the difference of an average global positioning system velocity and an average velocity computed by the inertial navigation system of the flight vehicles;

the difference of an incremental position of the global positioning system and the incremental position computed by the inertial navigation system of the flight vehicle;

the difference of a position of the global positioning system and a position computed by the inertial navigation system of the flight vehicle.

14. The system as recited in claim 9 wherein the in-flight alignment filter uses a Cartesian coordinate system or a coordinate system fixed to the body of the flight vehicle.

15. The system according to claim 13 wherein the in-flight alignment filter uses a linear function of alignment error, reference velocity error of the Doppler velocity sensor errors of the inertial sensor of the flight vehicle.

16. The system according to claim 15 wherein the reference velocity is global positioning system velocity, Doppler velocity system velocity measurement or velocity computed by the inertial navigation system of the flight vehicle and updated by the global positioning system.

17. A transfer alignment system for aligning an inertial navigation system of a slave vehicle comprising:

an inertial navigation system installed in the slave vehicle;

a Doppler velocity sensor installed in the slave vehicle and providing the velocity of the slave vehicle with respect to a coordinate system fixed to the body of the slave vehicle;

one of an inertial navigation system and an integrated global positioning system/inertial navigation system installed in an aircraft carrying the slave vehicle; and

a transfer alignment filter updated by a velocity measurement of the Doppler velocity sensor.